Publication Date:
2019-07-13
Description:
The design of the flutter suppression system for a remotely-piloted research vehicle is described. The modeling of the aeroelastic system, the methodology used to synthesized the control law, the analytical results used to evaluate the control law performance, and ground testing of the flutter suppression system onboard the aircraft are discussed. The major emphasis is on the use of optimal control techniques employed during the synthesis of the control law.
Keywords:
CYBERNETICS
Type:
NASA-TM-84642
,
NAS 1.15:84642
,
AIAA/ASME/ASCE/AHS 24th Struct., Struct. Dyn. and Mater. Conf.; May 02, 1983 - May 04, 1983; Lake Tahoe, NV; United States
Format:
application/pdf
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